Testing device for aircraft rotor system

Abstract

The utility model relates to a test device for an aircraft rotor system, belongs to the technical field of aircrafts, and is used for solving the problem that the test device in the prior art is difficult to simulate the load borne by the rotor system. The testing device for the aircraft rotor system comprises a tilting unit, a transmission speed reduction assembly and a waving unit, the transmission speed reduction assembly is connected with the tilting unit, one end of a pull rod of the rotor system is connected with the waving unit, and the other end of the pull rod penetrates through the transmission speed reduction assembly to be connected with the tilting unit; the waving unit comprises a head supporting piece, a waving assembly and a connecting base, the head supporting piece is hinged to the pull rod, and the connecting base is connected with the pull rod. The device can simulate the alternating impact load generated by the flapping movement of the paddle to the rotor system of the aircraft, and is simple and convenient to operate and simple in structure.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a test device for aircraft rotor systems. Background Technology

[0002] The rotor system of an aircraft is a key component that provides lift and thrust, and is widely used in vertical take-off and landing aircraft such as helicopters and multi-rotor drones.

[0003] The rotor system of an aircraft is the core rotating component and an important load-bearing component of the aircraft. It not only needs to bear the centrifugal force, flapping moment and oscillation moment transmitted from the blades, pitch shaft and rotor clips, but also needs to balance the pitch linkage load of the servo-swashplate system.

[0004] In the existing technology, when conducting fatigue tests on the core components of a rotor system, the complex force transmission structure and numerous sensor measurement points pose significant challenges to the loading of test loads and the debugging of equipment. Utility Model Content

[0005] Based on the above analysis, the present invention aims to provide a test device for aircraft rotor systems to solve the problem that existing test devices are difficult to simulate the loads on rotor systems.

[0006] The objective of this utility model is mainly achieved through the following technical solutions:

[0007] A test apparatus for an aircraft rotor system includes a tilting unit, a transmission and deceleration assembly, and a flapping unit. The transmission and deceleration assembly is connected to the tilting unit. One end of the rotor system's tie rod is connected to the flapping unit, and the other end passes through the transmission and deceleration assembly and is connected to the tilting unit.

[0008] The waving unit includes a head support, a waving assembly, and a connecting seat. The head support is hinged to the pull rod, and the connecting seat is connected to the pull rod.

[0009] The swinging assembly includes a rod end bearing, an adapter sleeve, a bushing, a shaft, and a spring. One end of the rod end bearing is connected to the head support, and the other end is connected to the shaft through the adapter sleeve. The spring is arranged around the shaft, and the shaft and the spring are disposed inside the bushing. The bushing is connected to the connecting seat.

[0010] Furthermore, the waving assembly also includes a limiting ring, which is disposed at both ends of the bushing and connected to the spring portion, allowing the shaft to move along the limiting ring.

[0011] Furthermore, a connecting ring is provided on the shaft, and the spring part includes a first spring and a second spring, both of which are connected to the connecting ring.

[0012] Furthermore, the first spring is disposed between the limiting retaining ring and the connecting ring at one end of the bushing, and the second spring is disposed between the limiting retaining ring and the connecting ring at the other end of the bushing.

[0013] Furthermore, it also includes a support assembly, which includes a base and a connecting rod, and the transmission reduction assembly includes a housing, which is connected to the base via the connecting rod.

[0014] Furthermore, the transmission reduction assembly also includes a reducer and a transmission component. The reducer is disposed within the housing and is connected to the motor via the transmission component.

[0015] Furthermore, the tilting unit includes a tilting connection assembly and an adjusting rod assembly. The tilting connection assembly includes a bearing connecting outer disk and a bearing inner ring. The bearing inner ring is disposed inside the bearing connecting outer disk and is connected to the bearing connecting outer disk. The pull rod is connected to the bearing inner ring. The adjusting rod assembly connects the bearing connecting outer disk to the housing.

[0016] Furthermore, the adjusting rod assembly includes a first threaded rod, a second threaded rod, and a threaded sleeve. The first threaded rod is connected to the housing, the second threaded rod is connected to the bearing connecting outer plate, and one end of the threaded sleeve is connected to the first threaded rod and the other end is connected to the second threaded rod.

[0017] Furthermore, the connecting seat is provided with a flange bearing and a fixing pin. The fixing pin is connected to the connecting seat, and the connecting seat can be connected to the tie rod through the fixing pin. The bushing is provided with a connecting head, and the connecting head is connected to the flange bearing through fixing bolts.

[0018] Furthermore, the waving assembly also includes a tension / compression sensor disposed between the head support and the shaft.

[0019] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0020] (1) The test device for aircraft rotor system of this utility model can simulate the alternating impact load generated by the blade flapping motion on the rotor system of the aircraft by setting up tilting unit and flapping unit, thereby enabling the fatigue strength test of the aircraft rotor system. It is easy to operate and has a simple structure.

[0021] (2) By setting the tilting connection component and the adjusting rod component, the tilting angle of the tilting unit can be adjusted, thereby driving the waving component to perform waving motion through the head support component, and simulating the actual working conditions of the rotor system.

[0022] (3) By setting up tension and compression sensors, the tension and compression forces on the rotor system during the test can be measured, thereby enabling the measurement of the complex motion forces of the rotor system's rotation and flapping. Attached Figure Description

[0023] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0024] Figure 1 This is a schematic diagram of the overall structure of the test device for an aircraft rotor system according to the present invention;

[0025] Figure 2 This is a schematic diagram of the tilting unit and transmission reduction assembly of this utility model;

[0026] Figure 3 This is a schematic diagram of the tilting unit of this utility model;

[0027] Figure 4 This is a schematic diagram of the waving unit of this utility model;

[0028] Figure 5 This is a schematic diagram of the structure of the connector of this utility model;

[0029] Figure 6 This is a schematic diagram of the waving component of this utility model.

[0030] Figure label:

[0031] 1-Support assembly; 11-Base; 12-Connecting rod; 2-Tilting unit; 21-Tilting connection assembly; 211-Bearing connecting outer plate; 212-Bearing inner ring; 22-Adjusting rod assembly; 221-First threaded rod; 222-Second threaded rod; 223-Threaded sleeve; 3-Transmission reduction assembly; 31-Reducer; 32-Transmission component; 33-Housing; 4-Waving unit; 41-Head support; 42-Waving assembly; 421-Rod end bearing; 422-Adapter sleeve; 423-Busset; 4231-Connector; 424-Shaft; 4241-Connecting ring; 425-Limiting retaining ring; 426-Spring part; 4261-First spring; 4262-Second spring; 427-Tension / compression sensor; 43-Connecting seat; 431-Flange bearing; 432-Fixing pin; 5-Pull rod. Detailed Implementation

[0032] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0033] A specific embodiment of this utility model discloses a test device for an aircraft rotor system, such as... Figures 1-2 As shown, the system includes a support assembly 1, a tilting unit 2, a transmission and deceleration assembly 3, and a waving unit 4. The support assembly 1 is connected to the transmission and deceleration assembly 3, and the transmission and deceleration assembly 3 is connected to the tilting unit 2. One end of the pull rod 5 of the aircraft rotor system is connected to the waving unit 4, and the other end passes through the transmission and deceleration assembly 3 and is connected to the tilting unit 2. The transmission and deceleration assembly 3 is connected to a motor, which drives the transmission and deceleration assembly 3 to rotate, thereby driving the pull rod 5 to rotate. The pull rod 5 then drives the waving unit 4 and the tilting unit 2 to move, thus simulating the load on the pull rod 5 during flight.

[0034] Furthermore, the support assembly 1 includes a base 11 and a connecting rod 12. The base 11 is connected to the connecting rod 12, and multiple connecting rods 12 are provided. The connecting rod 12 is detachably connected to the transmission reduction assembly 3.

[0035] Preferably, the base 11 is provided with a cavity, and the tilting unit 2 can enter the cavity of the base 11, thereby saving the space occupied by the test device.

[0036] For example, the connecting rod 12 is connected to the transmission reduction assembly 3 by bolts.

[0037] Furthermore, such as Figure 2 As shown, the transmission reduction assembly 3 includes a reducer 31, a transmission component 32, and a housing 33. The housing 33 is connected to the base 11 via a connecting rod 12, thereby keeping the housing 33 fixed relative to the base 11. The reducer 31 is disposed inside the housing 33 and connected to the housing 33 via a bearing seat, allowing the reducer 31 to rotate within the housing 33. The reducer 31 is connected to the motor via the transmission component 32, which transmits the rotational motion of the motor to the reducer 31. After the reducer 31 adjusts the speed, the motor's rotational motion is transmitted to the pull rod 5, thus simulating the actual rotational speed of the pull rod 5 during flight. The transmission component 32 transmitting the rotational motion of the motor to the reducer 31, and then the reducer 31 adjusting the speed before transmitting it to the pull rod 5, is existing technology and will not be described further here.

[0038] For example, the transmission component 32 is a transmission wheel.

[0039] like Figure 3As shown, the tilting unit 2 includes a tilting connection assembly 21 and an adjusting rod assembly 22. The tilting connection assembly 21 includes a bearing connecting outer disk 211 and a bearing inner ring 212. The bearing inner ring 212 is disposed inside the bearing connecting outer disk 211 and is connected to the bearing connecting outer disk 211 by a bearing. Multiple adjusting rod assemblies 22 are provided. The bearing connecting outer disk 211 is connected to the housing 33 through the adjusting rod assemblies 22. By controlling the length of the adjusting rod assemblies 22 at different positions, the tilting connection assembly 21 can be tilted. The pull rod 5 passes through the reducer 31 and is connected to the bearing inner ring 212. The bearing inner ring 212 can rotate with the pull rod 5 inside the bearing connecting outer disk 211.

[0040] Furthermore, the adjusting rod assembly 22 includes a first threaded rod 221, a second threaded rod 222, and a threaded sleeve 223. The first threaded rod 221 is connected to the housing 33 via a bearing seat, and the second threaded rod 222 is connected to the bearing connecting outer disk 211 via a bearing seat. One end of the threaded sleeve 223 is threadedly connected to the first threaded rod 221, and the other end is threadedly connected to the second threaded rod 222. By adjusting the distance that the first threaded rod 221 and / or the second threaded rod 222 are screwed into the threaded sleeve 223, the length of the adjusting rod assembly 22 can be adjusted. Thus, by controlling the length of the adjusting rod assembly 22 at different positions, the tilt angle of the tilting connection assembly 21 can be adjusted to simulate the load state of the tie rod 5.

[0041] Furthermore, such as Figures 4-5 As shown, the waving unit 4 includes a head support 41, a waving component 42, and a connecting seat 43. The head support 41 is hinged to the pull rod 5 and moves with the pull rod 5. Multiple waving components 42 are arranged around the pull rod 5. The head support 41 is connected to the waving component 42. The waving component 42 is fixedly connected to the connecting seat 43. The connecting seat 43 is fixedly connected to the pull rod 5 and can move with the pull rod 5.

[0042] It is understandable that when the tilting connection assembly 21 tilts at a certain angle, the head support 41 moves with the pull rod 5, causing the waving assembly 42 to perform a waving motion.

[0043] like Figures 4-6As shown, the waving assembly 42 includes a rod end bearing 421, an adapter sleeve 422, a bushing 423, a shaft 424, a retaining ring 425, and a spring part 426. One end of the rod end bearing 421 is connected to the head support member 41, and the other end is connected to the shaft 424 through the adapter sleeve 422. The spring part 426 is arranged around the shaft 424. The shaft 424 and the spring part 426 are arranged inside the bushing 423. The bushing 423 is fixedly connected to the connecting seat 43. Retaining rings 425 are provided at both ends of the bushing 423. The head support member 41 can drive the shaft 424 to move along the retaining ring 425. The spring part 426 is connected to the retaining ring 425. When the shaft 424 moves, the retaining ring 425 restricts the movement of the spring part 426, causing the spring part 426 to deform, simulating the alternating impact load of the blade waving motion on the head support member 41 and the pull rod 5.

[0044] For example, the two ends of the adapter sleeve 422 are threaded. One end of the adapter sleeve 422 is threaded to the rod end bearing 421, and the other end is threaded to the shaft 424. The rod end bearing 421 can drive the shaft 424 to move along the limiting ring 425 as the head support 41 moves.

[0045] For example, such as Figure 5 As shown, a flange bearing 431 and a fixing pin 432 are provided on the connecting seat 43. The fixing pin 432 is threadedly connected to the connecting seat 43. By tightening the fixing pin 432, the connecting seat 43 can be fixedly connected to the tie rod 5. A connector 4231 is provided on the bushing 423. The connector 4231 can be connected to the flange bearing 431 by fixing bolts, thereby fixing the bushing 423 to the connecting seat 43.

[0046] like Figure 6 As shown, a connecting ring 4241 is provided on the shaft 424. The connecting ring 4241 is fixedly connected to the shaft 424 and can move with the shaft 424. The spring part 426 includes a first spring 4261 and a second spring 4262. Both the first spring 4261 and the second spring 4262 are connected to the connecting ring 4241. The first spring 4261 is disposed between the limiting retaining ring 425 at one end of the bushing 423 and the connecting ring 4241, and the second spring 4262 is disposed between the limiting retaining ring 425 at the other end of the bushing 423 and the connecting ring 4241. When the shaft 424 is not under force, neither the first spring 4261 nor the second spring 4262 deforms.

[0047] Understandably, when the shaft 424 is pulled towards the head support 41 by the head support 41, the first spring 4261 is in a compressed state and the second spring 4262 is in a stretched state. The elastic force generated by the first spring 4261 and the second spring 4262 is transmitted to the pull rod 5 through the head support 41. When the shaft 424 is pushed away from the head support 41 by the head support 41, the first spring 4261 is in a stretched state and the second spring 4262 is in a compressed state. The elastic force generated by the first spring 4261 and the second spring 4262 is transmitted to the pull rod 5 through the head support 41, thereby using the elastic force generated by the first spring 4261 and the second spring 4262 to simulate the alternating impact load generated by the periodic flapping of the blade.

[0048] Preferred, such as Figure 5 As shown, the waving assembly 42 also includes a tension and compression sensor 427, which is disposed between the head support 41 and the shaft 424 and is used to measure the tension and compression forces on the rotor system during the test.

[0049] Compared with existing technologies, the experimental device for aircraft rotor systems of this invention, by setting up a tilting unit 2 and a flapping unit 4, can simulate the alternating impact load generated by the flapping motion of the rotor blades on the aircraft rotor system, thereby enabling the testing of the fatigue strength of the aircraft rotor system. By setting up a tilting connection assembly 21 and an adjusting rod assembly 22, the tilting angle of the tilting unit 2 can be adjusted, thereby driving the flapping assembly 42 to perform flapping motion via the head support 41, simulating the actual working conditions of the rotor system. By setting up a tension and compression sensor 427, the tension and compression forces acting on the rotor system during the test can be measured, thereby enabling the measurement of the complex kinematic forces of the rotor system's rotation and flapping motion.

[0050] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A test apparatus for an aircraft rotor system, characterized in that, It includes a tilting unit (2), a transmission and deceleration assembly (3) and a waving unit (4). The transmission and deceleration assembly (3) is connected to the tilting unit (2). One end of the rotor system's tie rod (5) is connected to the waving unit (4), and the other end passes through the transmission and deceleration assembly (3) and is connected to the tilting unit (2). The waving unit (4) includes a head support (41), a waving component (42), and a connecting seat (43). The head support (41) is hinged to the pull rod (5), and the connecting seat (43) is connected to the pull rod (5). The waving assembly (42) includes a rod end bearing (421), an adapter sleeve (422), a bushing (423), a shaft (424), and a spring part (426). One end of the rod end bearing (421) is connected to the head support (41), and the other end is connected to the shaft (424) through the adapter sleeve (422). The spring part (426) is arranged around the shaft (424). The shaft (424) and the spring part (426) are arranged inside the bushing (423). The bushing (423) is connected to the connecting seat (43).

2. The test apparatus for an aircraft rotor system according to claim 1, characterized in that, The waving assembly (42) also includes a limiting ring (425), which is disposed at both ends of the bushing (423). The limiting ring (425) is connected to the spring part (426), and the shaft (424) can move along the limiting ring (425).

3. The test apparatus for an aircraft rotor system according to claim 2, characterized in that, A connecting ring (4241) is provided on the shaft (424), and the spring part (426) includes a first spring (4261) and a second spring (4262), both of which are connected to the connecting ring (4241).

4. The test apparatus for an aircraft rotor system according to claim 3, characterized in that, The first spring (4261) is disposed between the limiting retaining ring (425) and the connecting ring (4241) at one end of the bushing (423), and the second spring (4262) is disposed between the limiting retaining ring (425) and the connecting ring (4241) at the other end of the bushing (423).

5. The test apparatus for an aircraft rotor system according to claim 1, characterized in that, It also includes a support assembly (1), which includes a base (11) and a connecting rod (12). The transmission and deceleration assembly (3) includes a housing (33), which is connected to the base (11) via the connecting rod (12).

6. The test apparatus for an aircraft rotor system according to claim 5, characterized in that, The transmission reduction assembly (3) further includes a reducer (31) and a transmission component (32). The reducer (31) is disposed inside the housing (33), and the reducer (31) is connected to the motor through the transmission component (32).

7. The test apparatus for an aircraft rotor system according to claim 5, characterized in that, The tilting unit (2) includes a tilting connection assembly (21) and an adjusting rod assembly (22). The tilting connection assembly (21) includes a bearing connecting outer disk (211) and a bearing inner ring (212). The bearing inner ring (212) is disposed inside the bearing connecting outer disk (211) and connected to the bearing connecting outer disk (211). The pull rod (5) is connected to the bearing inner ring (212). The adjusting rod assembly (22) connects the bearing connecting outer disk (211) to the housing (33).

8. The test apparatus for an aircraft rotor system according to claim 7, characterized in that, The adjusting rod assembly (22) includes a first threaded rod (221), a second threaded rod (222), and a threaded sleeve (223). The first threaded rod (221) is connected to the housing (33), the second threaded rod (222) is connected to the bearing connecting outer disk (211), one end of the threaded sleeve (223) is connected to the first threaded rod (221), and the other end is connected to the second threaded rod (222).

9. The test apparatus for an aircraft rotor system according to claim 1, characterized in that, The connecting seat (43) is provided with a flange bearing (431) and a fixing pin (432). The fixing pin (432) is connected to the connecting seat (43), and the connecting seat (43) can be connected to the tie rod (5) through the fixing pin (432). The bushing (423) is provided with a connector (4231), and the connector (4231) is connected to the flange bearing (431) by a fixing bolt.

10. The test apparatus for an aircraft rotor system according to any one of claims 1-9, characterized in that, The waving assembly (42) also includes a tension / compression sensor (427) disposed between the head support (41) and the shaft (424).

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